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  • 1
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    Manned Mars aerobrake vehicle design issues (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Space Technology - Industrial and Commercial Applications (ISSN 0892-9270); 12; 3; p. 313-324.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Advanced manned launch system study status (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Space Technology - Industrial and Commercial Applications (ISSN 0892-9270); 13; 3; p. 349-362.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Definition of an entry research vehicle (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 277-281
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced manned launch system study status (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Various concepts for advanced manned launch systems (AMLS) are examined for delivery missions to Space Station and polar orbit. Included are single- and two-stage winged systems with rocket and/or airbreathing propulsion systems. For near-term technologies, two-stage, reusable rocket systems are favored over single-stage rocket or airbreathing/rocket systems. Advanced technologies enable viable single-stage-to-orbit (SSTO) concepts. Although two-stage rocket systems continue to be lighter in dry weight than SSTOs, advantages in simpler operations may make SSTOs more cost-effective over the life cycle. Generally, rocket systems maintain a dry weight advantage over airbreathing systems at advanced technology levels, but to a lesser degree than when near-term technologies are used. More detailed understanding of vehicle systems and associated ground and flight operations requirements and procedures is essential in determining quantitative discrimination between these latter concepts.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: IAF PAPER 91-193
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Thrust vectoring for single-stage-to-orbit, horizontal takeoff, horizontal landing, space vehicles (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The preliminary design of a horizontal takeoff, horizontal landing, single-stage-to-orbit, rocket-powered space vehicle was performed. The purpose was to examine technology requirements for future small payload launch vehicles. The distinguishing aspect of the design was the utilization of thrust vectoring to provide half of the lift at takeoff. The inclusion of a canard was necessary to provide additional lift at takeoff and to balance the moments produced with thrust vectoring. A weights estimation, an aerodynamic assessment, a trajectory analysis, and a gear weight analysis were performed. The takeoff weight of the resulting vehicle was approximately 1.26 million pounds, based on advanced technology structures and subsystems. The vehicle was designed to deliver a 5000-pound payload to a polar orbit.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 86-1414
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Manned Mars aerobrake vehicle design issues (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper examines the preliminary definition of the stagnation region aerothermodynamic environment, the effect of convective/radiative effect of trim angle-of-attack mispredictions, packaging issues, and the implications of wake flow for vehicles not having an aft aeroshell. The implications of each of these factors for a Mars aerobrake configuration with a L/D in the range of 0.3-0.5 is evaluated. It is shown that packaging and wake flow requirements have a significant impact on the final design of a low L/D aerobrake. Due to the large proportion of carbonaceous species in the Martian atmosphere, radiative heating is seen to play a more dominant role in the stagnation region aerothermodynamics than for an equivalent earth entry. It is concluded that this radiation amplification is an additional reason to consider a multiple aerobrake system.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: IAF PAPER 90-197
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Design options for advanced manned launch systems (AMLS) (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Various concepts for advanced manned launch systems (AMLS) are examined for delivery missions to Space Station and polar orbit. Included are single- and two-stage winged systems with rocket and/or airbreathing propulsion systems. For near-term technologies, two-stage, reusable rocket systems are favored over single-stage rocket or two-stage airbreathing/rocket systems. Advanced technologies enable viable single-stage-to-orbit (SSTO) concepts. Although two-stage rocket systems continue to be lighter in dry weight than SSTOs, advantages in simpler operations may make SSTOs more cost effective over the life cycle. Generally, rocket systems maintain a dry weight advantage over airbreathing systems at the advanced technology levels, but to a lesser degree than when near-term technologies are used. More detailed understanding of vehicle systems and associated ground and flight operations requirements and procedures is essential in determining quantitative discrimination between these latter concepts.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 90-3816
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Electrostatic protection of the Solar Power Satellite and rectenna (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several features of the interactions of the solar power satellite (SPS) with its space environment were examined theoretically. The voltages produced at various surfaces due to space plasmas and the plasma leakage currents through the kapton and sapphire solar cell blankets were calculated. At geosynchronous orbit, this parasitic power loss is only 0.7%, and is easily compensated by oversizing. At low-Earth orbit, the power loss is potentially much larger (3%), and anomalous arcing is expected for the EOTV high voltage negative surfaces. Preliminary results of a three dimensional self-consistent plasma and electric field computer program are presented, confirming the validity of the predictions made from the one dimensional models. Magnetic shielding of the satellite, to reduce the power drain and to protect the solar cells from energetic electron and plasma ion bombardment is considered. It is concluded that minor modifications can allow the SPS to operate safely and efficiently in its space environment. The SPS design employed in this study is the 1978 MSFC baseline design utilizing GaAs solar cells at CR-2 and an aluminum structure.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-161438
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Static aerodynamic characteristics of a single-stage-to-orbit vehicle with low planform loading at Mach numbers from 0.3 to 4.63 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Transonic pressure and wind tunnel studies were performed to determine the longitudinal and lateral aerodynamic characteristics of a single-stage-to-orbit vehicle which utilizes an all metallic, hot structure, thermal protection system resulting in low planform loading. The model was tested over a Mach number range from 0.3 to 4.63 for angles of attack from -4 deg to 32 deg at both 0 deg and 5 deg sideslip.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-74056 , L-11797
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Supersonic dynamic-stability derivatives of the space shuttle launch vehicle (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made to determine the dynamic stability characteristics of a 0.015-scale model of the space shuttle launch vehicle at supersonic speeds. These tests were made at angles of attack from -10 deg to 10 deg at Mach numbers of 2.00, 2.86, 3.96, and 4.63. The complete launch vehicle, consisting of the orbiter, external tank, and solid rocket boosters, has positive damping in pitch, roll, and yaw over the angle-of-attack and Mach number range. The orbiter external tank configuration has a region of negative angles pitch damping for small negative of attack at a Mach number of 2.00. At all other test conditions, the orbiter external tank configuration has positive damping about all three axes.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-X-3315 , L-10494
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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